Aerospace and Electronic Systems Magazine July 2018 - 25

Shraim, Awada, and Youness
Table 6.

Disturbances Along the x-Axis
PID

Feedback
Linearization

Classical SM

Second
Order SM

Integral
Backstepping

Lyapunov

Unstable

2.8592

1.3226

0.5954

18.2138

1.2492

-

0.85

1

0.8

6.84

0.6

Unstable

4.2069

2.0219

0.8415

11.255

1.7891

-

1.82

1.5

1.4

4

1.1

Unstable

5.9384

2.9070

1.1955

9.4639

2.4725

-

0.82

0.98

0.8

2.06

0.8

PID

Feedback
Linearization

Classical SM

Second
Order SM

Integral
Backstepping

Lyapunov

Unstable

5.5641

1.2520

0.3138

8.8008

0.9409

-

0.6

0.75

0.5

>10

1.2

Unstable

4.2035

2.1636

0.4606

6.6632

1.3514

-

1.85

1.4

0.65

7.676

1.05

Unstable

6.3033

3.1815

0.6601

12.3286

1.9872

-

0.95

0.91

0.65

5.3

0.8

Disturbance at 10s
Peak (m)
Time to comeback (s)
Disturbance at 21s
Peak (m)
Time to comeback (s)
Disturbance at 44s
Peak (m)
Time to comeback (s)

Table 7.

Disturbances Along the y-Axis

Disturbance at 10s
Peak (m)
Time to comeback (s)
Disturbance at 21s
Peak (m)
Time to comeback (s)
Disturbance at 44s
Peak (m)
Time to comeback (s)

At this stage, we will study two subcriteria (Table 5), the
first is the insensibility of the controllers to the sudden variation of the speed and acceleration. The second is the insensibility of the controllers to the aggression and the difficulty of the
trajectory.
c. Controller robustness criterion:
The effect of external perturbations (wind disturbance) over a
small quadrotor may be important and lead to dangerous situations.
Thus, the study of robustness in the presence of disturbance is very
important. We have tested that by adding the disturbances over the
x axis (Table 6), y axis (Table 7), and z axis (Table 8) in many positions. Thus, the following table shows the peak that every controlJULY 2018

ler reached after the adding of disturbance and the time that it took
to return to the trajectory.
d. Energy efficiency criterion:
Outputs of controllers are the thrust and moments, which
achieve the desired mission. These values are related to the angular
velocity of each motor. The controller using the minimum amount
of energy will be the most efficient (Table 9).

CONCLUSION
Based on the comparative study done above, and if we make a
compromise between the subcriterion indicated above in the first

IEEE A&E SYSTEMS MAGAZINE

25



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